US10287908B2 - Variable orientation vane for compressor of axial turbomachine - Google Patents

Variable orientation vane for compressor of axial turbomachine Download PDF

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Publication number
US10287908B2
US10287908B2 US15/650,558 US201715650558A US10287908B2 US 10287908 B2 US10287908 B2 US 10287908B2 US 201715650558 A US201715650558 A US 201715650558A US 10287908 B2 US10287908 B2 US 10287908B2
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Prior art keywords
vane
magnetic field
control system
field source
control lever
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US20180045070A1 (en
Inventor
Stephane Hiernaux
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Safran Aero Boosters SA
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Safran Aero Boosters SA
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Assigned to SAFRAN AERO BOOSTERS SA reassignment SAFRAN AERO BOOSTERS SA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HIERNAUX, STEPHANE
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F04D29/323—Blade mountings adjustable
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F04D29/36—Blade mountings adjustable
    • F04D29/362—Blade mountings adjustable during rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/404—Transmission of power through magnetic drive coupling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y02T50/671—

Definitions

  • the invention relates to variable stator vanes.
  • the invention concerns a reduction in mechanical play in a system of variable stator vanes.
  • the invention also concerns an axial turbomachine, in particular an aircraft turbojet or turboprop engine, equipped with variable stator vanes.
  • vanes which are orientable relative to the housing of the turbojet compressor. Such vanes may be pivoted during operation of the engine. Their arched airfoil swivel relative to the primary flow which they cross, which allows their action to be adapted according to the engine speed and flight conditions. The operating range is thus extended.
  • vanes are equipped with control rods mounted so as to pivot in openings through the external casing of the compressor.
  • the free ends of the control rods are extended laterally by control levers which are themselves connected to a control ring.
  • Actuators allow the rings to be driven in rotation to incline the levers and hence orient the vanes.
  • the actuators may be controlled as a function of sensors or of different operating parameters of the turbomachine.
  • the performance of the compressor depends on the precision of angular positioning of the vanes relative to the casing. To this end, the coupling between the control rod and the lever of a vane must be precise as well as having to tolerate significant torque levels. The installation setting of the orientation between the control shaft and the lever must be particularly precise.
  • Document US2010/0166540 A1 discloses a turbomachine for an aircraft equipped with a compressor section.
  • the compression section comprises several rotor vanes and several stator vanes arranged upstream of the rotor vanes.
  • the compression section comprises a variable geometry thanks to the presence of pivoting stator vanes, which allows modification of the pressure and speed of the fluid supplied to the rotor vanes.
  • the pivoting vanes each comprise a journal extended by a control lever.
  • These control levers are connected to a common actuating ring which allows the assembly of the row of pivoting vanes to be controlled by simple rotation of the actuator ring.
  • each lever has a pincer form engaged with the associated vane, which limits the mechanical play harmful to the accuracy of control. However, mechanical play persists at the control ring. Also, the rotation of the latter causes a flexion of the levers and hence internal stresses in the levers.
  • the aim of the invention is to solve at least one of the problems posed by the prior art. More particularly, the aim of the invention is to improve the accuracy of control of a variable stator vane. Another aim of the invention is to propose a system for controlling variable stator vanes, reducing the play while limiting the internal stresses. A further aim of the invention is to propose a solution which is simple, resistant, lightweight, economic, reliable, easy to produce, simple to maintain and simple to inspect, and which improves efficiency.
  • the object of the invention is a control system for controlling a variable orientation vane of a turbomachine, the control system comprising: a support; a vane that is movable in rotation relative to the support and that comprises a lever for controlling the orientation of the vane; distinguished in that it also comprises an actuator with a magnetic field source which defines an air gap with the control lever so as to be able to drive the control lever in rotation.
  • the magnetic field source comprises a coil and where applicable a ferromagnetic core inside the coil.
  • the lever comprises a portion of ferromagnetic material cooperating with the magnetic field source.
  • the lever comprises an additional thickness cooperating with the magnetic field source.
  • the additional thickness is a radial additional thickness of the lever.
  • the vane comprises a chord, the length L of the lever being greater than or equal to half of the chord.
  • the magnetic field source is arranged in the plane of rotation of the lever.
  • the system comprises an elastic element configured to space the lever from the magnetic field source.
  • the system is adapted to power the magnetic field source electrically so as to move the lever progressively, in particular opposing the force exerted by the elastic element.
  • the support comprises a stop, the vane being movable in rotation between a first position against the stop and a second position against the magnetic field source, wherein the air gap can be closed when the vane is in the second position.
  • the vane comprises an airfoil intended to extend radially into a flow of the turbomachine from the support, the support separating the airfoil from the magnetic field source.
  • the system comprises a vane orientation sensor, the magnetic field source being controlled as a function of the orientation measured by the sensor.
  • the vane is a first vane
  • the lever is a first lever
  • the air gap is a first air gap
  • the control system also comprising a second vane which is movable in rotation relative to the support and which comprises a second lever for controlling the orientation of the second vane; the magnetic field source defining a second air gap with the second lever so as to drive the second lever in rotation.
  • the first vane comprises a first rotation axis
  • the second vane comprises a second rotation axis
  • the magnetic field source being arranged in a plane generated by the rotation axes.
  • the system comprises at least one annular row of identical variable orientation vanes; the first vane and the second vane belonging to the annular row, and each vane is movable in rotation relative to the support and comprises a control lever for controlling the orientation of the vane.
  • the system comprises at least two annular rows of variable orientation vanes; the first vane belonging to one of the two annular rows of vanes, and the second vane belonging to the other of the two annular rows of vanes.
  • the magnetic field source is arranged axially and/or circumferentially between the first vane and the second vane.
  • control system is configured so as to be able to turn the or each vane through an angle greater than or equal to 5°, or 10°, or 20°, or 30°.
  • the or each magnetic field source is arranged at the radial level of the associated lever.
  • the or each magnetic field source is an electromagnet and/or the electric field source drives the associated lever by electromagnetic induction.
  • the vane comprises a control rod passing through the support, the rod being mounted pivoting relative to the support.
  • the first vane and the second vane form a pair of vanes
  • the row consists of identical pairs of vanes, or the vanes of one of the two rows are identical to the first vane and the vanes of the other of the two rows are identical to the second vane.
  • each row of vanes is formed from identical vanes or identical pairs of vanes.
  • the length L of the lever is greater than or equal to half the spacing between two adjacent vanes of a same row and/or two successive orientable rows.
  • the system comprises a permanent magnet configured to space the or each associated lever from the magnetic field source; the permanent magnet can form a stop for the associated vane or for each associated vane.
  • the magnetic field source is arranged radially level with the magnetic field source.
  • a further object of the invention is a system for controlling a variable orientation vane(s) of a turbomachine, the control system comprising: a support, in particular an annular casing; a vane that is movable in rotation relative to the support and that comprises a lever for controlling the orientation of the vane; distinguished in that it also comprises a magnetic field source arranged in the trajectory of the lever and/or in the space swept by the lever so as to drive the lever in rotation, in particular directly.
  • the or each lever is straight or bent; where applicable made of one piece.
  • the invention also concerns a turbomachine comprising a system for controlling a variable orientation vane, in various instances the system conforms to the invention, for example the turbomachine comprises a low-pressure compressor in which the system is installed.
  • the turbomachine comprises a rotor with at least one annular row of rotor vanes arranged axially at the level of the or at least one magnetic field source.
  • the turbomachine is an aircraft turbojet or turboprop engine, the system being configured so as to power the or each magnetic field source electrically on take-off of the aircraft.
  • each object of the invention is also applicable to the other objects of the invention.
  • each object of the invention can be combined with the other objects.
  • the objects of the invention can also be combined with the embodiments of the description, which furthermore can be combined with each other.
  • the invention allows precise actuation of the orientable vanes. It reduces the number of movable interfaces, which extends the service life of the system despite the vibrations and temperature of the turbomachine.
  • the extreme positions of each orientable vane are furthermore respected. In fact, each field source forms a stop face which the vane reaches in its second position. This precision is achieved in a simple and economic fashion.
  • the invention also allows the magnetic field sources to be shared. This synergy reduces the mass and allows a saving.
  • the combination of springs and magnetic sources allows progressive control of the orientation of the vanes by progressive supply to the coils. In this way, each orientable vane can occupy a plurality of intermediate positions.
  • FIG. 1 depicts an axial turbomachine according to various embodiments of the invention.
  • FIG. 2 is a diagram of a compressor of the turbomachine according to various embodiments of the invention.
  • FIG. 3 illustrates a control system according to various first exemplary embodiments of the invention.
  • FIG. 4 illustrates a control system according to various second exemplary embodiments of the invention.
  • FIG. 5 illustrates a control system according to various third exemplary embodiments of the invention.
  • FIG. 6 illustrates a control system according to various fourth exemplary embodiments of the invention.
  • the terms “internal” and “external” refer to a positioning relative to the rotation axis of an axial turbomachine.
  • the axial direction corresponds to the direction along the rotation axis of the turbomachine.
  • the radial direction is perpendicular to the rotation axis.
  • Upstream and “downstream” refer to the main direction of the flow in the turbomachine.
  • FIG. 1 shows in simplified form an axial turbomachine.
  • the turbojet engine 2 comprises a first compression level called the low-pressure compressor 4 , a second compression level called the high-pressure compressor 6 , a combustion chamber 8 and one or more levels of turbines 10 .
  • the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets the two compressors 4 and 6 in motion.
  • the latter comprise several rows of rotor vanes associated with rows of stator vanes. Rotation of the rotor around its rotation axis 14 thus allows an air flow to be generated and progressively compressed until it enters the combustion chamber 8 .
  • An input fan 16 is coupled to the rotor 12 and generates an air flow which divides into a primary flow 18 passing through the various above-mentioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown), generating a thrust useful for propulsion of an aircraft.
  • FIG. 2 is a cross-sectional view of a compressor of an axial turbomachine as shown in FIG. 1 .
  • the compressor can be a low-pressure compressor 4 .
  • the rotor 12 comprises several rows of rotor vanes 24 , in this exemplary instance three.
  • the inclination of the chords of the rotor vanes 24 remains constant relative to the rotation axis 14 .
  • the low-pressure compressor 4 comprises several rectifiers, in this exemplary instance four, which each contain a row of stator vanes 26 and 28 in the sense that they are connected to the stator.
  • the rectifiers are associated with the fan 16 or with a row of rotor vanes to straighten the air flows so as to convert the flow speed into static pressure.
  • Each rotor or stator vane has a leading edge, a trailing edge, a front surface and a back surface; the surfaces connect the leading edge to the trailing edge, in the same way as the chords of the vane. In the description below, reference can be made to a median chord.
  • the front surface and back surface delimit the airfoil of the corresponding vane.
  • the stator vanes 26 and 28 extend substantially radially from an outer housing 30 .
  • the stator vanes 26 and 28 comprise inlet vanes 28 with fixed orientation and downstream vanes 26 with adjustable orientation. These vanes 26 are also known as variable stator vanes (VSV).
  • VSV variable stator vanes
  • the inclination of their chords can vary relative to the rotation axis 14 of the compressor 4 .
  • Their front and rear faces can be exposed to varying degrees to the primary flow 18 .
  • the orientable vanes 26 of a first row can be identical. In this exemplary instance, there are three rows of orientable vanes 26 . However, it would be possible to install further rows, for example by making the inlet vanes orientable. Or again, the compressor can comprise merely a single orientable row.
  • the orientable vanes 26 can pivot relative to the flow 18 such that their airfoils cover a varying proportion of the fluid flow. They can intercept the primary flow 18 to a greater extent. The circumferential width they occupy can vary. The leading edges and the trailing edges can move closer to or further away from the vanes of the same row. By being inclined to a varying extent relative to the general flow direction, they deflect the primary flow 18 to a greater or lesser extent in order to modulate the resulting flow rectification. Thus, the turbomachine and the compressor can be following different efficiency curves during operation.
  • the compressor 4 can comprise internal shrouds 32 suspended at the inner ends of the orientable vanes 26 . In order to allow their rotation, they have ends with pivot or ball connections (not shown). Thus, the orientable vanes 26 can also be inclined relative to the internal shrouds 32 .
  • the orientable vanes 26 carried by the casing 30 via the control rods 34 form rotatable connections.
  • Levers 36 at the tips of the rods 34 allow a rotation to be transferred to the orientable vanes 26 .
  • the angular orientations of the orientable vanes 26 are controlled by a control system 38 cooperating with the levers 36 .
  • the control system 38 comprises at least one magnetic field source 40 , in some exemplary instances several magnetic field sources 40 forming mechanical actuators. Each source 40 can be fixed to the outer surface of the casing 30 , which reduces the space required.
  • the control system 38 can comprise a magnetic field source 40 for each orientable vane, or one magnetic field source 40 for two orientable vanes 26 .
  • Each source 40 acts magnetically on one or more levers 36 by attraction or repulsion. This movement causes a rotation of the lever 36 concerned and hence a change in angular orientation of the corresponding orientable vane 26 .
  • FIG. 3 depicts a part of the control system 38 of FIG. 2 .
  • a row of rotor vanes 24 is represented by two vanes 24 .
  • the casing is not shown for reasons of clarity. Only two rows of orientable vanes 26 are shown for reasons of clarity. The operation of the row not shown can easily be deduced from the description below.
  • the orientable vanes 26 are each movable in rotation between a first position called the rest position (drawn in solid lines), and a second position called the active position (drawn in dotted lines). They pivot on themselves due to their control rods 34 . In the first position, the orientable vanes 26 can rest against angular stops 42 , for example formed on the casing. They can be held there thanks to elastic elements 44 such as springs, such that they can be auto-stable.
  • the levers 36 can be generally parallel to the chords of the orientable vanes 26 .
  • the levers 36 provide air gaps 46 with the source 40 .
  • the levers 36 have faces 48 facing the source 40 , the faces 48 delimiting the air gaps 46 .
  • These faces 48 can be formed on additional thicknesses 50 of the levers 36 .
  • the additional thicknesses 50 increase the useful surface area of the air gaps 46 , which increases the efficiency of the system.
  • the magnetic field produced in the air gaps 46 attracts the levers 36 such that the air gaps 36 close, and the faces 48 come into contact and hence rest against the source 40 .
  • the orientable vanes 26 thus come to stop against the sources 40 .
  • Each magnetic field source 40 can comprise an induction coil and optionally a ferromagnetic core inside the coil. This increases the magnetic field applied to the levers 36 . When the magnetic field source 40 is electrically powered, it produces a field which attracts the two levers 36 , causing the orientable vanes 26 to turn in the same direction.
  • each lever 36 can comprise a magnetic material. It can comprise a permanent magnet, a rare earth, a ferromagnetic material, steel and/or an organic material. The material can form each lever 36 integrally, or substantially the additional thicknesses 50 .
  • the source 40 can control two orientable vanes 26 . To do this, the source 40 is placed at the axial level of a row of rotor vanes 24 , which allows a radially compact installation.
  • FIG. 4 shows the control system 138 according to various second exemplary embodiments of the invention. This FIG. 4 repeats the numbering of the previous figures for identical or similar elements, the numbering being however incremented by 100. Specific numbers are added for this embodiment.
  • the control system 138 of these second exemplary embodiments is substantially identical to the first exemplary embodiments, but differs in that each orientable vane 126 is equipped with a dedicated magnetic field source 140 for each of the vanes of the corresponding row. This allows independent control of each orientable vane 126 .
  • the system 138 comprises an orientable vane 126 with a lever 136 transversely to its chord 152 .
  • the lever 136 can be perpendicular to the chord 152 .
  • the length L of the lever 136 can represent the majority of the length of the chord 152 .
  • the length L of the lever 136 can be measured from the end of the additional thickness 150 to the opposite end of the rod 134 .
  • the source 140 can be placed axially at the level of the associated orientable vane 126 .
  • the elastic element 144 is generally parallel to the rotation axis 114 .
  • FIG. 5 shows the control system 238 according to various third embodiments of the invention. This FIG. 5 repeats the numbering of the previous figures for identical or similar elements, the numbering being however incremented by 200.
  • the control system 238 of these third exemplary embodiments is substantially identical to the first exemplary embodiments. Nonetheless, it differs in that the source powers two orientable vanes 226 of the same annular row of vanes.
  • the two orientable vanes 226 receive between them a common magnetic field source 240 .
  • This source 240 is placed axially at the level of the orientable vanes 226 .
  • the levers 236 extend transversely relative to the chords of the orientable vanes 226 .
  • the levers 236 extend towards the other orientable vane 226 of the respective pair.
  • the present configuration offers axial compactness. It frees space at the level of the rotor vanes. The presence of annular fixing flanges is not hindered. The sharing of a same magnetic field source allows a reduction in the total number of sources and simplifies the control system.
  • one source can control four orientable vanes, for example two vanes of a first row and two vanes of a second row. These vanes describe a quadrilateral, the center of which receives the source.
  • This alternative can be achieved by combining the first exemplary embodiments of FIG. 3 with the third exemplary embodiments of FIG. 5 .
  • the person skilled in the art is encouraged to share each magnetic field source further.
  • FIG. 6 shows the control system 338 according to various fourth embodiments of the invention. This FIG. 6 repeats the numbering of the previous figures for identical or similar elements, the numbering being however incremented by 300.
  • the control system 338 of the fourth exemplary embodiments of the invention is similar to that of the second exemplary embodiments. Nonetheless it is distinguished in that a stop 342 is added to the control system 338 .
  • This stop 342 could cooperate with the lever 336 , in particular with the additional thicknesses 350 .
  • the stop is a permanent magnet.
  • the lever 336 and/or the additional thickness 350 comprise a ferromagnetic material, this magnet holds the vane 326 in its first position.
  • the source 340 When the source 340 is powered, it overcomes the holding force of the magnet and attracts the vane 326 into its second position.
  • the control system 338 of the fourth exemplary embodiments is substantially identical to the first exemplary embodiments, but differs however in that each orientable vane 326 is equipped with a dedicated magnetic field source 340 for each of the vanes of the corresponding row. This allows independent control of each orientable vane 326 .
  • the system 338 comprises an orientable vane 326 with a lever 336 transversely to its chord 352 .
  • the lever 336 can be perpendicular to the chord 352 .
  • the length L of the lever 336 can represent the majority of the length of the chord 352 .
  • the length L of the lever 336 can be measured from the end of the additional thickness 350 to the opposite end of the rod 334 .
  • the source 340 can be placed axially at the level of the associated orientable vane 326 .
  • the elastic element 344 is generally parallel to the rotation axis 314 .
  • a permanent magnet which can form a stop, can be provided for each vane according to each of the embodiments of the invention. It is possible that a same magnet can serve as a stop for two adjacent vanes.
  • Each spring can be replaced by a magnet.
  • Each spring can be configured to work in compression or in traction.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US15/650,558 2016-08-12 2017-07-14 Variable orientation vane for compressor of axial turbomachine Active 2038-01-22 US10287908B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
BE2016/5635 2016-08-12
BE2016/5635A BE1024492B1 (fr) 2016-08-12 2016-08-12 Aube a orientation variable de compresseur de turbomachine axiale

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US20180045070A1 US20180045070A1 (en) 2018-02-15
US10287908B2 true US10287908B2 (en) 2019-05-14

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EP (1) EP3282096B1 (fr)
BE (1) BE1024492B1 (fr)

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Publication number Priority date Publication date Assignee Title
CN112555193B (zh) * 2020-12-03 2021-07-23 吉林大学 一种角度可变的自调节式仿生风扇
BE1029457B1 (fr) 2021-06-04 2023-01-09 Safran Aero Boosters Ensemble de turbomachine d’aéronef, compresseur, turbomachine et procédé de détermination du calage angulaire d’aubes
BE1029455B1 (fr) 2021-06-04 2023-01-09 Safran Aero Boosters Ensemble de turbomachine d’aéronef, compresseur, turbomachine et procédé de détermination du calage angulaire d’aubes
BE1029454B1 (fr) 2021-06-04 2023-01-09 Safran Aero Boosters Ensemble de turbomachine d'aeronef, compresseur, turbomachine et procede de determination du calage angulaire d'aubes

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US20180045070A1 (en) 2018-02-15
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BE1024492B1 (fr) 2018-03-12
BE1024492A1 (fr) 2018-03-07

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